초록 ▼

An integrated engine control-autothrottle control system for controlling changes in the thrust of a jet aircraft engine during transients (i.e., changes in speed) in a manner that prevents throttle lead and overshoot (i.e., exceeds the response capability of the engine) is disclosed. The system uses

An integrated engine control-autothrottle control system for controlling changes in the thrust of a jet aircraft engine during transients (i.e., changes in speed) in a manner that prevents throttle lead and overshoot (i.e., exceeds the response capability of the engine) is disclosed. The system uses the engine control to continuously monitor current fuel flow (WF), burner pressure (PB), high rotor speed (N2) and engine thrust (EPR), manipulates the signals and produces limiting fuel flow transient error (WFPBERR) and rotor speed transient error (N2DOTERR) signals for both acceleration and deceleration. The lower parameter transient error signal is selected as the controlling limit signal during acceleration and the higher parameter transient error signal is selected as the controlling limit signal during deceleration. The controlling limit signals are used to produce limiting throttle lever angle rate of change signals－+TRADOT for acceleration and -TRADOT for deceleration. The throttle lever angle rate of change signals denote the maximum rate at which the throttle can be advanced (+TRADOT) or retarded (-TRADOT) without exceeding the response capabilities of the engines. The TRADOT signals are transmitted to the autothrottle and used to limit fuel flow changes so that the response capability of the aircraft is not exceeded.

대표청구항 ▼

A closed loop control system for controlling the autothrottle of an aircraft jet engine during transients in a manner that prevents the response capability of the engine from being exceeded, said closed loop control system comprising: (a) monitoring means for monitoring selected parameters of a jet

A closed loop control system for controlling the autothrottle of an aircraft jet engine during transients in a manner that prevents the response capability of the engine from being exceeded, said closed loop control system comprising: (a) monitoring means for monitoring selected parameters of a jet engine and producing related signals, said selected parameter signals including a core rotor speed (N2) signal, a fuel flow (WF) signal, and a pressure burner (PB) signal; (b) storage means for storing maximum rate of change of core rotor speed values based on core rotor speed values (N2DOTRFN), said storage means coupled to said monitoring means for receiving said N2 signal and, based on said N2 signal, producing a rotor speed transient error value (N2DOTERR) that denotes the maximum rate of change of core rotor speed acceptable by said jet engine without exceeding the response capability of the engine; (c) computation means coupled to said monitoring means and to said storage means for: (1) receiving said WF, PB and N2 signals and determining a fuel flow transient error value (WFPBERR) based on said WF, PB and N2 signals that denotes the rate of change in fuel flow acceptable by said jet engine without exceeding the maximum and minimum fuel flow to pressure burner ratios of the engine; (2) receiving N2DOTERR; and, (3) producing a throttle rate of change limit (TRADOT) signal having a magnitude that is selectively based on one or the other of N2DOTERR and WFPBERR.